Airworthiness Directives; Cessna Aircraft Company Models 172R, 172S, 182T, T182T, 206H, and T206H Airplanes, 18380-18383 [E7-6826]
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Federal Register / Vol. 72, No. 70 / Thursday, April 12, 2007 / Rules and Regulations
Installation of Cockpit Placard for RPM
Restriction
(f) Within 10 hours time-in-service (TIS)
after the effective date of this AD, install a
placard on the instrument panel as close to
the tachometer as possible, that states, in 1⁄8
inch-high or higher characters, ‘‘Continuous
operation between 2,350–2,450 RPM at or
above 24″ manifold pressure is prohibited’’.
The placard shall have red letters, on a
white contrasting background with a red
border. For example:
Continuous operation
between 2,350–2,450 RPM
at or above 24″ manifold
pressure is prohibited
Propellers With Unknown Total Hours TIS,
or 10,000 or More Hours Total TIS on the
Effective Date of This AD
(g) For propellers that the total TIS is
unknown, or that have 10,000 or more hours
total TIS on the effective date of this AD,
remove the propeller from service within 50
hours TIS after the effective date of this AD.
Propellers With Fewer Than 10,000 Hours
Total TIS on the Effective Date of This AD
(h) For propellers with fewer than 10,000
total hours TIS on the effective date of this
AD, do the following:
(1) Perform an inspection of the propeller
blades and repair if necessary, within 100
hours after the effective date of this AD,
using paragraphs 2.B. through 2.F. of
Accomplishment Instructions of McCauley
Propeller Systems Alert Service Bulletin
(ASB) No. ASB248, dated April 19, 2005.
(2) At the next propeller overhaul or next
major propeller disassembly, life-limit-stamp
the letter ‘‘L’’ on the propeller hub and
blades, using paragraph 3 of
Accomplishment Instructions of McCauley
Propeller Systems ASB No. ASB248, dated
April 19, 2005.
(3) Thereafter, within every 100 hours TIS
or at next annual inspection, whichever
occurs first, inspect, and repair if necessary,
the propeller blades using paragraphs 2.B.
through 2.F. of Accomplishment Instructions
of McCauley Propeller Systems ASB No.
ASB248, dated April 19, 2005.
(4) Remove the propeller from service upon
reaching the life limit of 10,000 hours total
TIS.
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Alternative Methods of Compliance
(i) The Manager, Wichita Aircraft
Certification Office, has the authority to
approve alternative methods of compliance
for this AD if requested using the procedures
found in 14 CFR 39.19.
Related Information
(j) Contact Jeff D. Janusz, Aerospace
Engineer, Wichita Aircraft Certification
Office, Small Airplane Directorate, 1801
Airport Road, Room 100, Wichita, KS 67209;
telephone: 316–946–4148, fax: 316–946–
4107, for more information about this AD.
Material Incorporated by Reference
(k) You must use McCauley Propeller
Systems Alert Service Bulletin No. ASB248,
dated April 19, 2005, to perform the actions
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14:18 Apr 11, 2007
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required by this AD. The Director of the
Federal Register approved the incorporation
by reference of this service bulletin in
accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. Contact McCauley Propeller Systems,
P.O. Box 7704, Wichita, Kansas; telephone
(800) 621–7767, for a copy of this service
information. You may review copies at the
FAA, New England Region, Office of the
Regional Counsel, 12 New England Executive
Park, Burlington, MA; or the National
Archives and Records Administration
(NARA). For information on the availability
of this material at NARA, call 202–741–6030,
or go to: https://www.archives.gov/federalregister/cfr/ibr-locations.html.
Issued in Burlington, Massachusetts, on
April 4, 2007.
Peter A. White,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E7–6831 Filed 4–11–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–27709; Directorate
Identifier 2007–CE–028–AD; Amendment
39–15020; AD 2007–08–03]
RIN 2120–AA64
Airworthiness Directives; Cessna
Aircraft Company Models 172R, 172S,
182T, T182T, 206H, and T206H
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) to
supersede AD 2006–17–04, which
applies to certain Cessna Aircraft
Company (Cessna) Models 172R, 172S,
182T, T182T, 206H, and T206H
airplanes. AD 2006–17–04 currently
requires you to inspect the two end
fittings on each of the flexible fuel hoses
located in the engine compartment for
the correct torque values, and, if any
incorrect torque values are found during
the inspection, tighten the hose end
fittings to the correct torque values. This
AD results from four reports of loose
fuel lines connected to the fuel servo or
fuel flow transducer. Two reports were
of in-flight engine failure on a Model
T182T airplane. A third report was of
in-flight engine failure on a Model 206H
airplane. A fourth report was of a Model
172S airplane losing engine power on
final approach. Consequently, this AD
would require you to establish the
correct torque values of the end fittings
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on fuel hoses for certain Cessna Models
172R, 172S, 182T, T182T, 206H, and
T206H airplanes. This AD clarifies that
the torque values need to be physically
established and visual inspection only
is not sufficient. We are issuing this AD
to detect and correct potential loss of
fuel flow, which may result in partial or
complete loss of engine power and/or
uncontrolled engine compartment fire
due to fuel leakage forward of the
firewall.
DATES: This AD becomes effective on
May 2, 2007.
On May 2, 2007 the Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in this AD.
We must receive any comments on
this AD by June 11, 2007.
ADDRESSES: Use one of the following
addresses to comment on this AD.
• DOT Docket Web site: Go to https://
dms.dot.gov and follow the instructions
for sending your comments
electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
0001.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
To get the service information
identified in this AD, contact The
Cessna Aircraft Company, Product
Support, P.O. Box 7706, Wichita,
Kansas 67277–7706; telephone: (316)
517–5800; facsimile: (316) 942–9006.
To view the comments to this AD, go
to https://dms.dot.gov. The docket
number is FAA–2007–27709;
Directorate Identifier 2007–CE–028–AD.
FOR FURTHER INFORMATION CONTACT:
Trenton Shepherd, Aerospace Engineer,
Wichita ACO, 1801 Airport Road, Room
100, Wichita, Kansas 67209; telephone:
(316) 946–4143; fax: (316) 946–4107.
SUPPLEMENTARY INFORMATION:
Discussion
One report of loose fuel hose
connections to the fuel injector servo on
a Cessna Model 172S airplane caused us
to issue AD 2006–17–04, Amendment
39–14725 (71 FR 47711, August 18,
2006). AD 2006–17–04 on certain
Cessna Models 172R, 172S, 182T,
T182T, 206H, and T206H airplanes,
currently requires you to:
• Inspect the two end fittings on each
of the flexible fuel hoses located in the
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Federal Register / Vol. 72, No. 70 / Thursday, April 12, 2007 / Rules and Regulations
engine compartment for the correct
torque values; and
• Tighten the hose end fittings to the
correct torque values, if any incorrect
torque values are found during the
inspection.
Since issuing AD 2006–17–04, we
have received four additional reports of
loose fuel lines connected to the fuel
servo or fuel flow transducer. Two
reports were of in-flight engine failure
on a Model T182T airplane. A third
report was of in-flight engine failure on
a Model 206H airplane. A fourth report
was of a Model 172S airplane that lost
engine power on final approach.
In issuing AD 2006–17–04, our intent
was for the torque values provided in
Table 4 of the AD to be verified.
However, the actions we specified in
AD 2006–17–04 resulted in visual-only
inspections being accomplished in some
cases. Visual inspection of torque paint
or putty is not sufficient to address the
unsafe condition. This AD clarifies that
the torque values need to be physically
established.
This condition, if not corrected, could
result in loss of fuel flow resulting in
partial or complete loss of engine power
and/or uncontrolled engine
compartment fire due to fuel leakage
forward of the firewall.
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Relevant Service Information
We reviewed Cessna Service Bulletin
No. SB07–71–01, original issue dated
March 2, 2007, Revision 1, dated March
16, 2007. The service information
describes procedures for a physical
inspection of the fuel hose connections
on each of the hoses by loosening each
connection and then reapplying the
correct torque value to make sure that
they are correctly torqued.
FAA’s Determination and Requirements
of This AD
We are issuing this AD because we
evaluated all the information and
determined the unsafe condition
described previously is likely to exist or
develop on other products of the same
type design. This AD requires you to
establish the correct torque values of the
end fittings on fuel hoses for certain
Cessna Models 172R, 172S, 182T,
T182T, 206H, and T206H airplanes.
This AD clarifies that the torque values
need to be physically established and
visual inspection only is not sufficient.
In preparing this rule, we contacted
type clubs and aircraft operators to get
technical information and information
on operational and economic impacts.
We did not receive any information
through these contacts. If received, we
would have included a discussion of
any information that may have
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14:18 Apr 11, 2007
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influenced this action in the rulemaking
docket.
FAA’s Determination of the Effective
Date
Since an unsafe condition exists that
requires the immediate adoption of this
AD, we determined that notice and
opportunity for public comment before
issuing this AD are impracticable, and
that good cause exists for making this
amendment effective in fewer than 30
days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not precede it by notice and an
opportunity for public comment. We
invite you to send any written relevant
data, views, or arguments regarding this
AD. Send your comments to an address
listed under the ADDRESSES section.
Include the docket number ‘‘Docket No.
FAA–2007–27709; Directorate Identifier
2007–CE–028–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the AD. We will consider all
comments received by the closing date
and may amend the AD in light of those
comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact we receive
concerning this AD.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this AD will not
have federalism implications under
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18381
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket that
contains the AD, the regulatory
evaluation, any comments received, and
other information on the Internet at
https://dms.dot.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The
Docket Office (telephone (800) 647–
5227) is located at the street address
stated in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2006–17–04, Amendment 39–14725 (71
FR 47711, August 18, 2006), and by
adding a new AD to read as follows:
I
2007–08–03 Cessna Aircraft Company:
Amendment 39–15020; Docket No.
FAA–2007–27709; Directorate Identifier
2007–CE–028–AD.
Effective Date
(a) This AD becomes effective on May 2,
2007.
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Federal Register / Vol. 72, No. 70 / Thursday, April 12, 2007 / Rules and Regulations
Affected ADs
Applicability
(c) This AD applies to the following
airplane models and serial numbers that are
certificated in any category:
(b) This AD supersedes AD 2006–17–04;
Amendment 39–14725.
TABLE 1.—APPLICABILITY
Model
Serial Nos.
(i) 172R ..............
(ii) 172S .............
17281244 through 17281364, 17281366 through 17281372, 17281374 through 17281376, and 17281379.
172S9809 through 172S10349, 172S10351 through 172S10374, 172S10376 through 172S10423, 172S10425 through
172S10426, 172S10428 through 172S10430, 172S10432 through 172S10444, 172S10446 through 172S10450, and
172S10452 through 172S10454.
18281527 through 18281889, 18281892, 18281895, 18281897, 18281899, 18281901, and 18281904.
T18208381 through T18208659, T18208661, T18208663 through T18208678, T18208680 through T18208686, T18208689,
and T18208690.
20608231 through 20608285.
T20608515 through T20608662, T20608664 through T20608697, T20608699 through T20608714, and T20608717.
(iii) 182T ............
(iv) T182T ..........
(v) 206H .............
(vi) T206H ..........
Unsafe Condition
(d) This AD is the result of four reports of
loose fuel lines connected to the fuel servo
or fuel flow transducer. Two reports were of
in-flight engine failure on a Model T182T
airplane. A third report was of in flight-
engine failure on a Model 206H airplane. A
fourth report was of a Model 172S airplane
that lost engine power on final approach. We
are issuing this AD to detect and correct
potential loss of fuel flow, which may result
in partial or complete loss of engine power
and/or uncontrolled engine compartment fire
due to fuel leakage forward of the firewall.
Compliance
(e) To address this problem, you must do
the following, unless already done:
TABLE 2.—ACTIONS, COMPLIANCE, AND PROCEDURES
Compliance
Procedures
(1) For all airplanes not equipped with the
Garmin G1000 System: Establish the correct
torque values of the end fittings on each of
the following hoses in the engine compartment:
(i) Fuel strainer to engine fuel pump.
(ii) Engine fuel pump to fuel injector servo
(except T206H).
(iii) T206H only: Engine fuel pump to the
union at the aft vertical cooling baffle.
(iv) T206H only: Union at the aft vertical
cooling baffle to the fuel injector servo.
(v) Fuel injector servo to fuel manifold
valve (except turbo models).
(vi) Turbo models only: Fuel injector servo
to fuel flow transducer.
(vii) Turbo models only: Fuel flow transducer to fuel manifold valve.
(viii) Fuel injector servo fuel return to firewall fitting.
(2) For all airplanes equipped with the Garmin
G1000 System: Establish the correct torque
values of the end fittings on each of the following hoses in the engine compartment:
(i) Fuel strainer to engine fuel pump.
(ii) Engine fuel pump to fuel injector servo
(except T206H).
(iii) T206H only: Engine fuel pump to the
union at the aft vertical cooling baffle.
(iv) T206H only: Union at the aft vertical
cooling baffle to the fuel injector servo.
(v) Fuel injector servo to fuel flow transducer.
(vi) Fuel flow transducer to fuel manifold
valve.
(vii) Fuel injector servo fuel return to firewall fitting.
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Actions
Within the next 5 hours time-in-service (TIS)
after May 2, 2007 (the effective date of this
AD).
Follow Cessna Service Bulletin No. SB07–71–
01, Revision 1, dated March 16, 2007; the
procedures of the appendix to this AD; and
the torque values from the table Torque
Values for Hose End Fittings in the appendix to this AD.
Within the next 5 hours TIS after May 2, 2007
(the effective date of this AD).
Follow Cessna Service Bulletin No. SB07–71–
01, Revision 1, dated March 16, 2007; the
procedures of the appendix to this AD; and
the torque values from the table Torque
Values for Hose End Fittings in the appendix to this AD.
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Federal Register / Vol. 72, No. 70 / Thursday, April 12, 2007 / Rules and Regulations
Special Flight Permit
(f) Under 14 CFR 39.23, we are allowing
special flight permits for the purpose of
compliance with this AD under the following
conditions: Only operate under day visual
flight rules (VFR).
Alternative Methods of Compliance
(AMOCs)
(g) The Manager, Wichita Aircraft
Certification Office (ACO), FAA, ATTN:
Trenton Shepherd, Aerospace Engineer,
Wichita ACO, 1801 Airport Road, Room 100,
Wichita, Kansas 67209; telephone: (316) 946–
4143; fax: (316) 946–4107, has the authority
to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Before using any approved AMOC on any
airplane to which the AMOC applies, notify
your appropriate principal inspector (PI) in
the FAA Flight Standards District Office
(FSDO), or lacking a PI, your local FSDO.
(h) AMOCs approved for AD 2006–17–04
are not approved for this AD.
Material Incorporated by Reference
(i) You must use Cessna Service Bulletin
No. SB07–71–01, Revision 1, dated March 16,
2007, to do the actions required by this AD,
unless the AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact The Cessna Aircraft
Company, Product Support, P.O. Box 7706,
Wichita, Kansas 67277–7706; telephone:
(316) 517–5800; facsimile: (316) 942–9006.
(3) You may review copies at the FAA,
Central Region, Office of the Regional
Counsel, 901 Locust, Kansas City, Missouri
64106; or at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Appendix to AD 2007–08–03—
Inspection Instructions—Cessna
Aircraft Company Models 172R, 172S,
182T, T182T, 206H, and T206H
Airplanes
1. Remove upper and side cowlings to
perform torque procedure.
2. Remove all signs of old torque putty or
paint.
3. Using a suitable tool loosen the hose end
fitting of each joint, while using a suitable
tool to restrain the other end fitting of the
joint to preclude rotation.
4. Using the applicable fitting torque from
the table Torque Values for Hose End Fittings
of this appendix to AD 2007–08–03, torque
the hose end fitting to the proper torque,
while using a suitable tool to restrain the
other end fitting of the joint to preclude
rotation.
5. After proper torque has been applied to
the hose end fitting, apply the applicable
torque paint or putty to the hose end fitting
joint.
6. If during any torque procedure any of
the non-hose end fittings rotate, stop the
torque procedure. Totally disconnect the
hose end joint and remove any fitting that
has rotated. After the cleaning, visual
examination, and/or replacement of the
fitting and/or any seals or sealant, reinstall
the fitting and torque it to the applicable
requirement. Then reconnect the hose end
fitting and repeat Step 4. of this appendix to
AD 2007–08–03.
7. Use the table below Torque Values for
Hose End Fittings for the correct torque
values to tighten the hose end fittings as
required in paragraphs (e)(1) and (e)(2) of this
AD:
TORQUE VALUES FOR HOSE END FITTINGS
Correct torque in inch-pounds
Flare hex sizes in fractions of an inch
Hose size
Minimum
¥4
¥6
¥8
⁄
................................................................................................................................................
..............................................................................................................................................
7⁄8 .................................................................................................................................................
9 16
⁄
11 16
Issued in Kansas City, Missouri, on April
5, 2007.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. E7–6826 Filed 4–11–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2007–27110; Airspace
Docket No. 07–AGL–1]
Modification of Class E Airspace; Peru,
IL
Federal Aviation
Administration (FAA), DOT.
ACTION: Direct final rule; confirmation
of effective date.
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AGENCY:
SUMMARY: This document confirms the
effective date of the direct final rule
which revises Class E airspace at Peru,
IL.
VerDate Aug<31>2005
14:18 Apr 11, 2007
Jkt 211001
EFFECTIVE DATE:
0901 UTC, May 10,
2007.
FOR FURTHER INFORMATION CONTACT:
Grant Nichols, System Support, DOT
Regional Headquarters Building, Federal
Aviation Administration, 901 Locust,
Kansas City, MO 64106; telephone (816)
329–2522.
The FAA
published this direct final rule with a
request for comments in the Federal
Register on February 26, 2007 (72 FR
8266). The FAA uses the direct final
rulemaking procedures for a noncontroversial rule where the FAA
believes that there will be no adverse
public comment. This direct final rule
advised the public that no adverse
comments were anticipated, and that
unless a written adverse comment, or a
written notice of intent to submit such
an adverse comment, were received
within the comment period, the
regulation would become effective on
May 10, 2007. No adverse comments
were received, and thus this notice
confirms that this direct final rule will
become effective on that date.
SUPPLEMENTARY INFORMATION:
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Maximum
135
270
450
150
300
500
Issued in Forth Worth, Texas, on March 21,
2007.
Ronnie L. Uhlenhaker,
Manager, System Support Group, ATO
Central Service Area.
[FR Doc. 07–1803 Filed 4–11–07; 8:45 am]
BILLING CODE 4910–13–M
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2006–25997; Airspace
Docket No. 06–ANM–5]
Revision of Class E Airspace;
Redmond, OR
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: This action will revise the
Class E airspace at Redmond, OR.
Additional Class E airspace is necessary
to accommodate aircraft using a new
Area Navigation (RNAV) Global
Positioning System (GPS) Standard
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]]>Agencies
[Federal Register Volume 72, Number 70 (Thursday, April 12, 2007)]
[Rules and Regulations]
[Pages 18380-18383]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-6826]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-27709; Directorate Identifier 2007-CE-028-AD;
Amendment 39-15020; AD 2007-08-03]
RIN 2120-AA64
Airworthiness Directives; Cessna Aircraft Company Models 172R,
172S, 182T, T182T, 206H, and T206H Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) to
supersede AD 2006-17-04, which applies to certain Cessna Aircraft
Company (Cessna) Models 172R, 172S, 182T, T182T, 206H, and T206H
airplanes. AD 2006-17-04 currently requires you to inspect the two end
fittings on each of the flexible fuel hoses located in the engine
compartment for the correct torque values, and, if any incorrect torque
values are found during the inspection, tighten the hose end fittings
to the correct torque values. This AD results from four reports of
loose fuel lines connected to the fuel servo or fuel flow transducer.
Two reports were of in-flight engine failure on a Model T182T airplane.
A third report was of in-flight engine failure on a Model 206H
airplane. A fourth report was of a Model 172S airplane losing engine
power on final approach. Consequently, this AD would require you to
establish the correct torque values of the end fittings on fuel hoses
for certain Cessna Models 172R, 172S, 182T, T182T, 206H, and T206H
airplanes. This AD clarifies that the torque values need to be
physically established and visual inspection only is not sufficient. We
are issuing this AD to detect and correct potential loss of fuel flow,
which may result in partial or complete loss of engine power and/or
uncontrolled engine compartment fire due to fuel leakage forward of the
firewall.
DATES: This AD becomes effective on May 2, 2007.
On May 2, 2007 the Director of the Federal Register approved the
incorporation by reference of certain publications listed in this AD.
We must receive any comments on this AD by June 11, 2007.
ADDRESSES: Use one of the following addresses to comment on this AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590-0001.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
To get the service information identified in this AD, contact The
Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita,
Kansas 67277-7706; telephone: (316) 517-5800; facsimile: (316) 942-
9006.
To view the comments to this AD, go to https://dms.dot.gov. The
docket number is FAA-2007-27709; Directorate Identifier 2007-CE-028-AD.
FOR FURTHER INFORMATION CONTACT: Trenton Shepherd, Aerospace Engineer,
Wichita ACO, 1801 Airport Road, Room 100, Wichita, Kansas 67209;
telephone: (316) 946-4143; fax: (316) 946-4107.
SUPPLEMENTARY INFORMATION:
Discussion
One report of loose fuel hose connections to the fuel injector
servo on a Cessna Model 172S airplane caused us to issue AD 2006-17-04,
Amendment 39-14725 (71 FR 47711, August 18, 2006). AD 2006-17-04 on
certain Cessna Models 172R, 172S, 182T, T182T, 206H, and T206H
airplanes, currently requires you to:
Inspect the two end fittings on each of the flexible fuel
hoses located in the
[[Page 18381]]
engine compartment for the correct torque values; and
Tighten the hose end fittings to the correct torque
values, if any incorrect torque values are found during the inspection.
Since issuing AD 2006-17-04, we have received four additional
reports of loose fuel lines connected to the fuel servo or fuel flow
transducer. Two reports were of in-flight engine failure on a Model
T182T airplane. A third report was of in-flight engine failure on a
Model 206H airplane. A fourth report was of a Model 172S airplane that
lost engine power on final approach.
In issuing AD 2006-17-04, our intent was for the torque values
provided in Table 4 of the AD to be verified. However, the actions we
specified in AD 2006-17-04 resulted in visual-only inspections being
accomplished in some cases. Visual inspection of torque paint or putty
is not sufficient to address the unsafe condition. This AD clarifies
that the torque values need to be physically established.
This condition, if not corrected, could result in loss of fuel flow
resulting in partial or complete loss of engine power and/or
uncontrolled engine compartment fire due to fuel leakage forward of the
firewall.
Relevant Service Information
We reviewed Cessna Service Bulletin No. SB07-71-01, original issue
dated March 2, 2007, Revision 1, dated March 16, 2007. The service
information describes procedures for a physical inspection of the fuel
hose connections on each of the hoses by loosening each connection and
then reapplying the correct torque value to make sure that they are
correctly torqued.
FAA's Determination and Requirements of This AD
We are issuing this AD because we evaluated all the information and
determined the unsafe condition described previously is likely to exist
or develop on other products of the same type design. This AD requires
you to establish the correct torque values of the end fittings on fuel
hoses for certain Cessna Models 172R, 172S, 182T, T182T, 206H, and
T206H airplanes. This AD clarifies that the torque values need to be
physically established and visual inspection only is not sufficient.
In preparing this rule, we contacted type clubs and aircraft
operators to get technical information and information on operational
and economic impacts. We did not receive any information through these
contacts. If received, we would have included a discussion of any
information that may have influenced this action in the rulemaking
docket.
FAA's Determination of the Effective Date
Since an unsafe condition exists that requires the immediate
adoption of this AD, we determined that notice and opportunity for
public comment before issuing this AD are impracticable, and that good
cause exists for making this amendment effective in fewer than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not precede it by notice and an opportunity for
public comment. We invite you to send any written relevant data, views,
or arguments regarding this AD. Send your comments to an address listed
under the ADDRESSES section. Include the docket number ``Docket No.
FAA-2007-27709; Directorate Identifier 2007-CE-028-AD'' at the
beginning of your comments. We specifically invite comments on the
overall regulatory, economic, environmental, and energy aspects of the
AD. We will consider all comments received by the closing date and may
amend the AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact we
receive concerning this AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket that contains the AD, the regulatory
evaluation, any comments received, and other information on the
Internet at https://dms.dot.gov; or in person at the Docket Management
Facility between 9 a.m. and 5 p.m., Monday through Friday, except
Federal holidays. The Docket Office (telephone (800) 647-5227) is
located at the street address stated in the ADDRESSES section. Comments
will be available in the AD docket shortly after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2006-17-04, Amendment 39-14725 (71 FR 47711, August 18, 2006), and by
adding a new AD to read as follows:
2007-08-03 Cessna Aircraft Company: Amendment 39-15020; Docket No.
FAA-2007-27709; Directorate Identifier 2007-CE-028-AD.
Effective Date
(a) This AD becomes effective on May 2, 2007.
[[Page 18382]]
Affected ADs
(b) This AD supersedes AD 2006-17-04; Amendment 39-14725.
Applicability
(c) This AD applies to the following airplane models and serial
numbers that are certificated in any category:
Table 1.--Applicability
------------------------------------------------------------------------
Model Serial Nos.
------------------------------------------------------------------------
(i) 172R...................... 17281244 through 17281364, 17281366
through 17281372, 17281374 through
17281376, and 17281379.
(ii) 172S..................... 172S9809 through 172S10349, 172S10351
through 172S10374, 172S10376 through
172S10423, 172S10425 through 172S10426,
172S10428 through 172S10430, 172S10432
through 172S10444, 172S10446 through
172S10450, and 172S10452 through
172S10454.
(iii) 182T.................... 18281527 through 18281889, 18281892,
18281895, 18281897, 18281899, 18281901,
and 18281904.
(iv) T182T.................... T18208381 through T18208659, T18208661,
T18208663 through T18208678, T18208680
through T18208686, T18208689, and
T18208690.
(v) 206H...................... 20608231 through 20608285.
(vi) T206H.................... T20608515 through T20608662, T20608664
through T20608697, T20608699 through
T20608714, and T20608717.
------------------------------------------------------------------------
Unsafe Condition
(d) This AD is the result of four reports of loose fuel lines
connected to the fuel servo or fuel flow transducer. Two reports
were of in-flight engine failure on a Model T182T airplane. A third
report was of in flight-engine failure on a Model 206H airplane. A
fourth report was of a Model 172S airplane that lost engine power on
final approach. We are issuing this AD to detect and correct
potential loss of fuel flow, which may result in partial or complete
loss of engine power and/or uncontrolled engine compartment fire due
to fuel leakage forward of the firewall.
Compliance
(e) To address this problem, you must do the following, unless
already done:
Table 2.--Actions, Compliance, and Procedures
----------------------------------------------------------------------------------------------------------------
Actions Compliance Procedures
----------------------------------------------------------------------------------------------------------------
(1) For all airplanes not equipped Within the next 5 hours time-in- Follow Cessna Service Bulletin No.
with the Garmin G1000 System: service (TIS) after May 2, 2007 SB07-71-01, Revision 1, dated March
Establish the correct torque values (the effective date of this AD). 16, 2007; the procedures of the
of the end fittings on each of the appendix to this AD; and the torque
following hoses in the engine values from the table Torque Values
compartment: for Hose End Fittings in the
(i) Fuel strainer to engine fuel appendix to this AD.
pump.
(ii) Engine fuel pump to fuel
injector servo (except T206H).
(iii) T206H only: Engine fuel
pump to the union at the aft
vertical cooling baffle.
(iv) T206H only: Union at the
aft vertical cooling baffle to
the fuel injector servo.
(v) Fuel injector servo to fuel
manifold valve (except turbo
models).
(vi) Turbo models only: Fuel
injector servo to fuel flow
transducer.
(vii) Turbo models only: Fuel
flow transducer to fuel
manifold valve.
(viii) Fuel injector servo fuel
return to firewall fitting.
(2) For all airplanes equipped with Within the next 5 hours TIS after Follow Cessna Service Bulletin No.
the Garmin G1000 System: Establish May 2, 2007 (the effective date of SB07-71-01, Revision 1, dated March
the correct torque values of the this AD). 16, 2007; the procedures of the
end fittings on each of the appendix to this AD; and the torque
following hoses in the engine values from the table Torque Values
compartment: for Hose End Fittings in the
(i) Fuel strainer to engine fuel appendix to this AD.
pump.
(ii) Engine fuel pump to fuel
injector servo (except T206H).
(iii) T206H only: Engine fuel
pump to the union at the aft
vertical cooling baffle.
(iv) T206H only: Union at the
aft vertical cooling baffle to
the fuel injector servo.
(v) Fuel injector servo to fuel
flow transducer.
(vi) Fuel flow transducer to
fuel manifold valve.
(vii) Fuel injector servo fuel
return to firewall fitting.
----------------------------------------------------------------------------------------------------------------
[[Page 18383]]
Special Flight Permit
(f) Under 14 CFR 39.23, we are allowing special flight permits
for the purpose of compliance with this AD under the following
conditions: Only operate under day visual flight rules (VFR).
Alternative Methods of Compliance (AMOCs)
(g) The Manager, Wichita Aircraft Certification Office (ACO),
FAA, ATTN: Trenton Shepherd, Aerospace Engineer, Wichita ACO, 1801
Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-
4143; fax: (316) 946-4107, has the authority to approve AMOCs for
this AD, if requested using the procedures found in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
(h) AMOCs approved for AD 2006-17-04 are not approved for this
AD.
Material Incorporated by Reference
(i) You must use Cessna Service Bulletin No. SB07-71-01,
Revision 1, dated March 16, 2007, to do the actions required by this
AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact The
Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita,
Kansas 67277-7706; telephone: (316) 517-5800; facsimile: (316) 942-
9006.
(3) You may review copies at the FAA, Central Region, Office of
the Regional Counsel, 901 Locust, Kansas City, Missouri 64106; or at
the National Archives and Records Administration (NARA). For
information on the availability of this material at NARA, call 202-
741-6030, or go to: https://www.archives.gov/federal_register/code_
of_federal_regulations/ibr_locations.html.
Appendix to AD 2007-08-03--Inspection Instructions--Cessna Aircraft
Company Models 172R, 172S, 182T, T182T, 206H, and T206H Airplanes
1. Remove upper and side cowlings to perform torque procedure.
2. Remove all signs of old torque putty or paint.
3. Using a suitable tool loosen the hose end fitting of each
joint, while using a suitable tool to restrain the other end fitting
of the joint to preclude rotation.
4. Using the applicable fitting torque from the table Torque
Values for Hose End Fittings of this appendix to AD 2007-08-03,
torque the hose end fitting to the proper torque, while using a
suitable tool to restrain the other end fitting of the joint to
preclude rotation.
5. After proper torque has been applied to the hose end fitting,
apply the applicable torque paint or putty to the hose end fitting
joint.
6. If during any torque procedure any of the non-hose end
fittings rotate, stop the torque procedure. Totally disconnect the
hose end joint and remove any fitting that has rotated. After the
cleaning, visual examination, and/or replacement of the fitting and/
or any seals or sealant, reinstall the fitting and torque it to the
applicable requirement. Then reconnect the hose end fitting and
repeat Step 4. of this appendix to AD 2007-08-03.
7. Use the table below Torque Values for Hose End Fittings for
the correct torque values to tighten the hose end fittings as
required in paragraphs (e)(1) and (e)(2) of this AD:
Torque Values for Hose End Fittings
----------------------------------------------------------------------------------------------------------------
Correct torque in inch-pounds
Flare hex sizes in fractions of an inch Hose size -------------------------------
Minimum Maximum
----------------------------------------------------------------------------------------------------------------
\9/16\.......................................................... -4 135 150
\11/16\......................................................... -6 270 300
\7/8\........................................................... -8 450 500
----------------------------------------------------------------------------------------------------------------
Issued in Kansas City, Missouri, on April 5, 2007.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. E7-6826 Filed 4-11-07; 8:45 am]
BILLING CODE 4910-13-P
